Aeroplane



A. H. ROSS Oct 15, 1929.

AEROPLANE Filed Jan. 21, 1928 2 Sheets-Sheet 11 Inventor v 141 mm BossAttornqy A. H. RUSS AEHOPLANE Opt. 15, 1929.

Filed Jan. 21, 1928 2 Shasta-Sheet 2 talented 15, 1929 ATENT oFFicaanuoruan'u Application filed January at The present invention relates toaeroplanes and has for its object toprovide a structure which is capableof flotation on water and has means incorporated therein so that watermay 5 be taken into a compartment formed in the tail'for the purpose ofgiving the plane proper equilibrium on the water. lt is now the commonpractice to mount the heavier portions of an aeroplane such as theengine in the'nose. thereof while the tail carries comparatively littleweight. The result is that if an aeroplane lands on the water it has atendency to nose downwardly but with my improvement sufficient wateristaken in the tail to overcome this tendency.

Another very important object of the invention resides in the provisionofan aeroplane which has the engine and gasoline tank so arrangedtherein as to give the properequilibrium to the aeroplane when flying.

Another very important object of the invention resides in the'provisionof wings of hollow construction for containing a supply of helium andthe heating of the helium so as to attain maximum elhciency.

it still further very important object of the invention resides in theprovision of an aeroplane of this nature which is comparatively simplein its construction, strong and durable, thoroughly eficient andreliable in operation, and otherwise well adapted to the purpose forwhich it is designed.

With the above and numerous other objects M in view as will appear asthe description pro- J s o I a ceeds the invention resides 1n certainnovel features of construction, and in the combination and arrangementof parts as will be hereinafter more fully described and claimed.

llu the drawings:

Figure 1 is a side elevation of an aeroplane embodying the features ofmy invention,

Figure 2 is a fragmentary detail transversesection taken substantiallyon the line at 2-2 of Figure 1,

all

. formed therei teas. Serial No. aaaaoa.

Figure 3 is an enlarged detail section taken substantially on the line 33' of Figure 1.,

Figure 4: is a vertical longitudinal section through the aeroplane,Figure 5 is anenlarged detail section showin the water receivingcompartment of the tail, and Y Figure 6 is an enlarged detail sectiontaken substantially on the line 66 of Figure l.

Referring to the drawings in detail itwill be seen that the fuselage Fis of the stream line type comprising the'nose 5, the operatorscompartment 6 and the tail 7. The aeroplane illustrated herein is of themonoplane type but I do not wish to belimited to this particular type.The wings 8 are hollow as illus trated to advantage in Figure 3 so thata supply of helium may be stored therein. The passenger compartment 6has a doorway 10 n with a door 11 thatmay be held tightly therein as isillustrated to advantage in Figure 6. The door is provided with interioroffset flanges 12 so that paclrving 13 may be placed thereon to engagethe e fuselage easily about lnterlor surface of th y 10. Bearings 14 aredisposed on the offset flanges 12 and rockably receive a shaft 15 havingcams 16 on the ends thereof. to engage in brackets 17 on the inside ofthe compartment 6. A crank 18 is provided at the center of the shaft 15for manipulation thereof. The compartment 6 is also provided with apluralityof port holes 20 which may be closed by transparent portclosures 21 which are held in place bycrank shafts 22 having cams 23 toengage flanges 24 and hold them with their packing 25 tightly againstthe interior surface of the compartment. The crank shafts arerockable inbearings 26. An engine 27 is mounted .in the nose for driving propeller28. A gasoline tank 29 is mounted on the lower portion of the nose and avacuum system 30 connects the tank 29 with the carbu-reter of theengine. A reserve asoline tank 31 is mounted in the tail immediately toe0 the doorwa the rear of the compartment 6 and is connected by a pipe32 with. the tank 29 and a valve 33 is mounted in the pipe 32 andoperable from an accessible position to the aviator. A filler pipe 34rising from the tank 31 so as to be accessible from the top of the tail.The

partition 35 is provided longitudinally of the tail 7 to form acompartment 36. The portion of the tail wall about the compartment 36 isformed with openings. 37 for receiving plates 38 having openings 39therein and cages 40- thereon for projecting inwardly of the ecompartment 36. Ball valves 41 are mounted in the cages 40 to close theopenings 39 normally by gravitation.

When the aeroplane lands on the water it will be seen that thecompartment 36 will fill because the ball valves 41 are constructed ofcork or some other floatable material. The water trapped in thecompartment 36 will give the proper stability to the aeroplane on gine27 and other heavier parts located at the front thereof.

A pipe 42 leading from the exhaust of the engine 27 is led through theWings 8.

The heat from the pipe 42 Will heat the helium and increase theeffectiveness thereof.

Control wires 24 for the rudder 45 and other elements lead through thefuselage to the control sticks 46.

It is thought that a clear understanding of I themain proportions of theaeroplane will now be understood. The compartment 6 is defined bypartitions 47 and 48 which terminate a distance from the top of thecompartment so-that access may be had to the tail and to the nose forobvious purposes, A port 20 is provided in'the top of the compartment 6-and has a hinged port closure 21 mounted therein so that the same may beopened when the fuselage is floating on the water so that the occupantsin the compartment may have proper air.

The present embodiment of the invention has been disclosed inconsiderable detail merely by way of example since in actual the waterto overcome the weight of the en- 7 4 practice it attains the featuresof advantage enumerated as desirable in the statement of the inventionand the above description. It will be apparent that changes in thedetails of construction, and in the'combination and arrangement of partsmay be resorted to without departing from the spirit or scope ofthdinvention as hereinafter claimed or. sac- IlfiClIlg any of itsadvantages.

Having thus described my invention,,what I claim as new is:

In an aeroplane structure comprising a fuselage, a partition in thefuselage at the tail portion thereof .to form a compartment extendinglongitudinally along the bottomthereof, said tail Havin openings leadingin the compartment thus, ormed, plates in said openings wlth cagesextending inwardly

